Aeroplane



' June 21, 1932. F. L. JANS-0N 1,864,438

AEROPLANE Filed Feb. 4, 1931 ll ll A tlorney Patented June 21,` 1932 I YUNITED fs'm'rlazsl PATENT ori-ICE FREDERICK LESTER Janson, or roarCHESTER, Naw Yom:

momma Application meu :february 4, mi. smal m. 513,409.

This invention relates to aeroplanes in geninvention resides inthecertain novel coneral, but more particularly to a means for struction,combination and arrangement of preventing the accumulation of ice uponthe parts, the essential features of which are herewing tips of aircrafts of the heavier-than-air 'inafter fully described, areparticularly type. v y pointed out in the appended claims, and are 55 Itis a well known fact that an aeroplane illustrated inthe accompanyingdrawing, in iying through the elements in a freezing or which: belowfreezing temperature is subjected to ex- Figure 1 is a fragmentary topplan view of treme danger by reason of snow, sleet, or ice an aeroplanewith a portion of the wing l0 accumulating upon the wing structure. Thisstructure broken away. o0

not only increases the weight of the craft, but Figure 2 is afragmentary plan view of one tends to interfere with the control thereof0f the tip ends of the wing with parts broken which is vital to .thesafety of the craft and away in section. I

those carried thereby. It is therefore the v Figure 3 is a fragmentarytop plan view of principal object of this invention to subject a portionof the wing with parts broken awa 66 surfaces of the wing structure on-which ice, 1n section to illustrate the manner in which snow and sleetare most likely to accumulate the'exhaust heated gases are directed inop oto the action of heat of a temperature` above site directions asthey enter the wing heatlng the freezing point while the craft is iniiight, chamber.

and which heat is derived from the exhaust Figure 4 is an enlargedvertical transverse lo gases of the internal combustion engine orsectional view on the line 4 4 of Figure 1. engines by which the craftis propelled. Figure 5 is a vertical transverse sectional Another objectof the invention resides in view illustrating a modified form of myincausing the heated exhaust'gases of the air vention. 2i craft engineto pass through the wings simul- Referring to the drawing by reference75 taneously in opposite directions from a point characters, andparticularly to Figure 1 of substantially centrally between the ends ofthe drawing, the reference numeral l'desigthe wing tocause aproportionate amount of nates the internal combustion engine hof anheated gases to pass to the atmosphere aeroplane A of theheavier-than-air type. through the tip ends of the wing. By this arrlheair craft also includes the usual wing 2 80 rangement both sides of thewings are kept which extends transversely of the fuselage 3. atsubstantially the same degree of tempera- The wing structure -2 may beof the presture, and an even exhaust pressure is mainent hollow metallicconstruction, and mounttained at the tip ends to assure stability of edwithin the same and extending substantial- 3 the craft at all times. lyparallel to the leading edge 4 of the wing 85 Another object is toprovide a simple means is a partition 5 which is preferably of a heatfor directing the heat generated by an aeroresisting or insulatingmaterialsuch as as plane engine into a. plurality of tabs along thebestes or the like. This partition is secured 40 leading edge of theaeroplane wing. in position by brackets or like elements 6 A furtherobject is the provision of an which are bolted or riveted to the top andaeroplane wing heating system which maybe bottom walls of the wing 2.The partition installed on metallic wing structures now in 5 inconjunction with the walls of the leaduse without requiring radicalchanges in the ing edge 4 of the wing cooperate to proconstructionthereof. vide a heat compartment or passageway 7 A still further objectof the invention rewhich opens through the outer ends of the sides in anaeroplane wing heating system wing through openings 8.

which also actssas a muffler for the exhaust A pipe 9 has one endconnected to the gases yfrom the propelling internal combusmanifold 10of the internal combustion ention engine. 1 y gine 1, while the oppositeend of the said pipe With thesesand other objects in view, the Aisflared-outwardly as at 11 and is flxedly se- 10 cured to the leadingedge of the wing at a pointA approximately centrally thereof, and whichpipe 9 opens into the passageway or heat compartment 7 Forthe purpose ofdirecting the iow of the heated exhaust gases toward opposite ends-ofthe wing structure, I provide a substantially V-shaped deecting member12, the pointed end of which extends into the iared portion 11 of thepipe 9 to divide the outlet end of the pipe 41l into two separatelpassages, and to likewise divide the heat chamber 7 into two separateconduits or passages 13-13. By this arrangement, it will be seen that aproportionate amount of the heated gases from the engine are caused -topass to the respective conduits 13-13 to heat the Walls of the leadingedge 4 of the wing structure. After passing out through opposite ends ofthe wing, the exhaust gases are deected rearwardly by reason of deectormembers or shields 14 Which are carriedby opposite ends of the wing.These shield members 14 are of convex configuration exteriorly andconcaved interiorly., and are disposed in spaced relation to the opening8, but in substantial alinement with the said openings 8 for the purposeof deflecting the exhaust gases rearwardly as shown in dotted lines inFigure 2 of the drawing'. This shield or protector member prevents aircurrents in the region of the wing tip from swirling into the outlet ofthe exhaust passages which would otherwise produce an undesirable backpressure therein. The shield members also serve to produce a vacuumadjacent the openings 8 to induce the passage of the exhaust gases fromthe manifold of the engine toward the discharge end 8 of the passages13.

From the foregoing description, it will be understood that the heatedexhaust gases from the internal combustion engine of the air craft arepassed through the conduit 13 simultaneously and which gases move inopposite directions toward the tip ends of the wings. The heat fromthese gases acts on the walls of the leading edge of the wings andprevent the possible assumulation of ice, snow, or sleet thereon.

In Figure 5 of the drawing I have illustrated a slightly modified formof my 'invention in which the numeral 15 designates aY wing structure ofthe same type. as that shown in the preferred form. In this form Iprovide a longitudinally extending partition 16 of asbestos or otherinsulating material which is held in spaced relation with respect to theleading edge 17 of the wing, and the top wall 18 of the said wing. Byspacing the partition with respect to the leading edge in the top wall,I provide a heat chamber 19 within the wing, and which is adapted toreceive the exhaust gases from an internal combustion engine in the samemanner as explained in the preferred form. vFor the purpose of securingthe partition 16 in position, I employ brace brackets or elements 20which are suitably positioned to securely hold and position thepartition in spaced relation with respect to the parts above referredto. In this form, not only the leading edge of the wingisjfsubjccted tothe action of heat, but also the'top of the Wing structure is heated toprevent the accumulation of undesirable deposits thereon.

In addition to the functions of the heat conduits embodied in the wings,the same act as mufflers for deading the explosion of the aeroplanemotor.

It Will be readily apparent from the above description that thisvinvention is capable of being readily applied to aeroplane wings andbody structures which have already been constructed, as well as simplyand economically incorporating the same in an aeroplane Wing in theprocess of manufacture. The arrangement proposed is simple andinexpensive, as well as of great utility, permitting the utilization ofthe exhaust from the aeroplane motor in the heating of an aeroplane wingto prevent accumulation of ice or sleet thereon. By employing thedei'lecting member at the entrance end to the heat conduit, the exhaustgases are guided without loss into the two branches of the heatingchamber, and without back pressure being set up on the exhaust pipe.Furthermore the outlet openings at the tip ends of the wing areprotected by the shield members which permit the establishment of asuction force at the discharge openings and prevent a back pressurecaused by wind current in the neighborhood of the wing tips.

While I have shown and described what I deem to be the most desirableembodiment of my invention, it will be understood that various changesin construction, may be resorted to if desired, and I do not limitmyself to the precise structural details herein set forth, nor toanything less than the whole of my invention, limited only by theappended claims.

Having thus described the invention, what I claim as new and desire tosecure by Letters Patent is 1. In combination with an air craft having apropelling internal combustion engine, a wing having a passage extendinglengthwise thereof and opening through its end, means for conveyingheating exhaust gases from said engine to said passageway to heat thewalls thereof during the passage of the heated gases therethrough, andprotecting shield members carried 'by opposite ends of said wings andextending outward beyond the open ends of the passageway but disposed inalinement therewith.v

2. In combination with an aeroplane having an internal combustionengine, and a hollow wing, a partition )Nithin said hollow wingextending the length thereof to form a passage along the leading edge ofthe win sald passage opening through opposite en of said wing, and meansfor conveying .heated exhaust gases from said engine to said passage ata point intermediate its ends, and deiector members extending beyondopposite ends of said wings in the path of the gases exhausted throughopposite'ends of said passage. e 3. In combination with an aeroplane,having a propelling engine and a. metallic wing having a passage thereinextending substantially the length thereof and openmg to the atmosphere,means to conduct exhaust gases from the engine into the passage, theassage being defined by the top and the lea 'ng edge portions of thewing and a partition 2o member of heat insulating material in the wingspaced from said leading edge, and a shield member carried by said Wingand overlying the open ends of said passage.

In testimony whereof, I have hereto affixed my signature.

- FREDERICK L. JAN SON.

